AD 2024-04-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | SAS | Airworthiness Directives; Airbus SAS Airplanes |
| aircraft | Aviat | Various | Airworthiness Directives; Airbus SAS Airplanes |
Unsafe Condition
Cracking of the fastener holes in certain fuselage frames, specifically at the four holes of the crossbeam splicing at frame (FR)16 and FR20 on both the left-hand (LH) and right-hand (RH) sides, which can result in reduced structural integrity of the airplane due to the failure of structural components.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Continue to require repetitive inspections for cracking of the fastener holes in certain fuselage frames. Depending on airplane configuration, provide an optional terminating action to the repetitive inspections, as specified in EASA AD 2023-0150. Allow the use of applicable previously issued Alternative Methods of Compliance (AMOCs).
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the compliance times specified in EASA AD 2023-0150, which are incorporated by reference.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Airbus SAS Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.